US 12,072,100 B1
Combustor for a gas turbine engine
Pradeep Naik, Bengaluru (IN); Shai Birmaher, Cincinnati, OH (US); Saket Singh, Bengaluru (IN); Narasimhan Suresh Sahana, Bengaluru (IN); and Kwanwoo Kim, Cincinnati, OH (US)
Assigned to GENERAL ELECTRIC COMPANY, Cincinnati, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Nov. 7, 2023, as Appl. No. 18/503,751.
Int. Cl. F23R 3/14 (2006.01); F02C 3/30 (2006.01); F23R 3/00 (2006.01); F23R 3/16 (2006.01)
CPC F23R 3/14 (2013.01) [F02C 3/30 (2013.01); F23R 3/002 (2013.01); F23R 3/16 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A combustor for an aircraft gas turbine engine, the combustor comprising:
a dome structure;
a swirler assembly connected to the dome structure; and
a cowl connected to the dome structure and defining a plenum between the dome structure and the cowl, and surrounding the swirler assembly, the cowl including an airflow opening through an upstream wall portion of the cowl for providing a flow of compressed air into the plenum, wherein the cowl includes a cowl steam channel therewithin and a plurality of steam injection nozzles that provide a flow of steam from the cowl steam channel into the plenum.